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Spacecraft reconfigurable power supply system architecture

A technology for power supply systems and spacecraft, applied in the direction of control/regulation systems, instruments, collectors, etc., to achieve high reliability, flexible architecture, and improved specific power

Active Publication Date: 2019-08-20
SHANGHAI INST OF SPACE POWER SOURCES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there are few studies on the topology of reconfigurable power systems at home and abroad, and the application of domestic reconfigurable power systems in aerospace is still in a blank stage.

Method used

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  • Spacecraft reconfigurable power supply system architecture
  • Spacecraft reconfigurable power supply system architecture
  • Spacecraft reconfigurable power supply system architecture

Examples

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Embodiment Construction

[0011] Specific examples are used below to illustrate the specific implementation of the present invention, and those skilled in the art can easily understand the advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented and applied through other different specific implementation modes, and various modifications and changes can be made to the details in this specification based on different application occasions and requirements without departing from the spirit of the present invention.

[0012] In order to describe the technical content, structural features, achieved goals and effects of the present invention in detail, the following will be described in detail in conjunction with the embodiments and accompanying drawings.

[0013] see figure 1 , the present invention proposes a reconfigurable power supply system architecture for spacecraft, which specifically includes solar array modules 1...

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Abstract

The invention provides a spacecraft reconfigurable power supply system architecture comprising a solar cell array, a storage battery pack, a source bus, a function switch module, a DC / DC converter module and a load bus. The solar cell array and the storage battery pack are taken as a source electrode and are connected to a segmented source busbar through the function switch module, and the sourcebus is connected to the load bus through the DC / DC converter module to realize energy conversion. The DC / DC converter has the ability to reconstitute a MPPT module, a battery charging module, a battery discharging module and other functional modules, the switching of various working modes of a power supply system is carried out the function switch module and a reconstruction algorithm, the defectsof fixed module, non-variable function and large system of a traditional spacecraft power system module are solved, and the power system output capability upgrade, energy expansion upgrade, fault reconfiguration and modular design are achieved. The architecture is simple and flexible and has high reliability.

Description

technical field [0001] The invention relates to the field of spacecraft power supply system design, in particular to the architecture and work mode design of a power supply system with modular and reconfigurable functions. Background technique [0002] For spacecraft systems with a large difference between constant power and peak power, such as probes with electric propulsion, the power requirements for normal working conditions and short-term acceleration processes are not at the same level. According to the design method of the traditional solar power plus battery power system, the power level of the circuit should be designed according to the maximum power demand, resulting in a large system, lower utilization rate, and higher cost, which is not conducive to improving specific power. [0003] The power reconfigurable technology can reconfigure the same circuit into different functions under different functional requirements of the system, improve the utilization rate of t...

Claims

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Application Information

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IPC IPC(8): H02J7/35H02M3/158
CPCH02J7/35H02M3/1582Y02E10/56
Inventor 王飞龙周光锐黄渠森张兴浩彭方涛徐泽锋刘勇
Owner SHANGHAI INST OF SPACE POWER SOURCES
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